Abstract: A rotor disc 2 is provided with blade receiving recesses 40 at its outer periphery. The disc 2 has an internal cavity 34 for conveying cooling air to blades 4 retained in the recesses 40. Each blade-receiving recess 40 intersects the cavity 34 to provide communication between the cavity 34 and the recesses 40. The disc 2 may be made from separate disc components 12, 14 which define the cavity 34 between them.

Abstract: A rotor disc 2 is provided with blade receiving recesses 40 at its outer periphery. The disc 2 has an internal cavity 34 for conveying cooling air to blades 4 retained in the recesses 40. Each blade-receiving recess 40 intersects the cavity 34 to provide communication between the cavity 34 and the recesses 40. The disc 2 may be made from separate disc components 12, 14 which define the cavity 34 between them.

Abstract: Mounting discs (20, 30, 40, 50) are used in gas turbine engines to present turbine or compressor blades. These discs (20, 30, 40, 50) incorporate a bore or cob end 31, 41, 51 which in turn previously had a flat end face surface. Such flat end face surfaces are weight efficient but can lead to reduced component life and a limitation with regard to rotational speed due to Von-Mises stresses. By providing a deviation (39, 49, 59, 69) in the end face from a flat aspect, a reduction in axial stress is achieved with a marginal increase in hoop stress but with a net result that there is a reduction in the general operational Von-Mises stresses and therefore improvement in disc life or potential rotation speed capacity or both.